Abstract: A vibrotactile system for an aircraft may comprise a plurality of tactors and a tactor driver operably coupled to the plurality of tactors. The tactor driver may be configured to determine a vibration sequence for the plurality of tactors in response to a signal received from an aircraft controller, and to send vibration commands corresponding to the vibration sequence to the plurality of tactors.

Abstract: An optical system is disclosed. The optical system includes collimating optics, including a polarization beam splitter, which includes one or more polarizations selection reflection surfaces configured to split image light into (s)-polarized light and (p)-polarized light. The collimating optics further include a first mirror configured to receive and reflect (p)-polarized light emitted from the one or more polarization selective reflection surfaces, a second mirror configured to receive and reflect (s)-polarized light emitted from the one or more polarization selective reflection surface, and a corrector lens configured to receive (p)-polarized light reflected from the first mirror and receive (s)-polarized light reflected from the second mirror, wherein a light path of the (s)-polarized light and a light path of the (p)-polarized light are substantially equal, wherein the (p)-polarized light and the (s)-polarized light are configured to combine to form a user image.

Abstract: A method is disclosed. The method may include receiving chart data; converting the received chart data into one or more sets of hardware directives and one or more subroutines, the one or more sets of one or more hardware directives including at least a first set hardware directives and a second set of hardware directives, the first set of hardware directives including one or more relative offsets needing address modification, the second set of hardware directives not needing address modification; generating a display list including the set of hardware directives and one or more rules, the one or more relative offsets needing address modification arranged at a beginning position in the generated display list; providing the generated display list to an on-board aircraft controller; and updating, via the on-board aircraft controller, the one or more absolute addresses of the relative offsets of the first set of hardware directives during run-time.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: receiving, via the processor, an ejection command for ejecting an ejection seat from an aircraft; determining, via the processor, an aircraft or ejection seat altitude and an aircraft or ejection seat speed; and commanding, via the processor, a simultaneous or staged deployment of a drogue parachute and a main parachute upon or just prior to separation of the ejection seat from the aircraft, the simultaneous or staged deployment being described herein.

Abstract: A system may include a display and a processor. The processor may be configured to: obtain aircraft data associated with an aircraft; obtain or generate storm top data, the storm top data including information associated with storm top altitudes and storm top locations; generate aircraft relative storm top data; generate an aircraft relative storm top image based at least on the aircraft relative storm top data, wherein the aircraft relative storm top image depicts a view of weather in front of the aircraft, wherein the aircraft relative storm top image conveys information associated with a difference between at least some of the storm top altitudes and an altitude of the aircraft; and output the aircraft relative storm top image as graphical data.

Abstract: A rehosted flight operation system is disclosed. The system comprises one or more controllers configured to execute program instructions. The program instructions include a rehosted flight operation module configured to generate one or more emulated flight operation subsystems, and a host flight operation module configured to generate flight operation data and flight operation commands.

Abstract: A system and method for a multi-beam multi-function active electronically scanned array (AESA) radar operation receives radar commands from individual aircraft systems and segments a single AESA fixed panel into a plurality of subarrays to carry out each individual function commanded by the individual aircraft system. Dependent on aircraft status and phase of flight, the subarrays are sized based on desired radar function at the specific phase of flight and specific threat associated with the phase. The system dynamically shifts the subarray size, beam characteristics, power settings, and function to enable multiple function of a cost effective single AESA panel.

Abstract: A method for determining an operational geographical zone relative to a sensor may include a step of simulating the position of said sensor; a step of determining a first zone of the region of interest; and a step of determining a second zone of the region of interest. The region of interest of the first zone may be constituted by points at each of which said object at that point traveling at a speed greater than or equal to said speed VT and in a given direction, would be seen by the sensor as having a radial speed greater than a threshold speed defined for that point. The operational geographical zone. may be defined by taking account of the intersection of the first zone and of a coverage zone of the sensor.

Abstract: A system may include a tactical military network including tactical nodes and a tactical gateway node configured as a trusted network access node (TNAN) to a mobile core network. The system may further include a military trusted interworking function (M-TIF) device of the mobile core network. The M-TIF device may support an interworking function between the tactical military network and the mobile core network. The M-TIF device may be communicatively coupled to the tactical gateway node. The tactical gateway node may be collocated with the M-TIF device. Services of the mobile core network may be accessible to the tactical nodes via the tactical gateway node and the M-TIF device.

Abstract: A system and method for detection and identification of an Unmanned Aircraft Systems (UAS) employs a radar system to detect and identify the UAS based on the rich Doppler spectrum generated by one or more rotors and associated motors onboard the UAS. UAS have a low radar cross sections (RCS), relatively low speed, and possess a unique Doppler signature providing data for the system to discriminate once the system detects the quadcopter UAS. The system and method functions as a traditional radar, yet analyzes the micro-Doppler signature, including the RCS and radial speed, to detect and identify the UAS. Based on the signature analysis, the system and method are able to distinguish one model from other types of UAS.

Abstract: An electronic checklist system is disclosed. The system configured to acquire an electronic checklist (ECL), the ECL including a plurality of tasks, each task including a command sequence including one or more command items. The system configured to display the plurality of tasks via a display and receive an initiation input via a user interface. The system configured to transmit one or more communications configured to initiate a performance of one or more automatable actions corresponding to the tasks, the one or more automatable actions configured to at least one of change or measure one or more system states. The system configured to receive system state data. The system configured to display, based on the system state data, one or more completion status graphics indicative of a completion of at least a portion of the plurality of tasks.

Abstract: An ejection seat may comprise a seatback, a headrest located at an upper end of the seatback, and a pitot tube rotatably coupled to the headrest. A pitot restraint assembly may be operably coupled to the pitot tube. The pitot restraint assembly may be configured to translate between a restrained state and a released state. The pitot tube may rotate from a stowed position to a deployed position in response to the pitot restraint assembly translating to the released state.

Abstract: An imaging system for an aircraft is disclosed. A plurality of image sensors are attached, affixed, or secured to the aircraft. Each image sensor is configured to generate sensor-generated pixels based on an environment surrounding the aircraft. Each of the sensor-generated pixels is associated with respective pixel data including, position data, intensity data, time-of-acquisition data, sensor-type data, pointing angle data, latitude data, and longitude data. A controller generates a buffer image including synthetic-layer pixels, maps the sensor-generated pixels to the synthetic-layer pixels in the buffer image, fills a plurality of regions of the buffer image with the sensor-generated pixels, and presents the buffer image on a head-mounted display (HMD) to a user of the aircraft.

Abstract: A system comprising a head worn display and an image rendering computing device is disclosed. The head worn display comprises one or more image sensors, a head position sensor, and a head position computing device configured to determine a first head pose. The image rendering computing device is configured to render an enhanced image and embed the first head pose in the enhanced image. The head position computing platform is further configured to determine a second head pose, determine a difference between the second head pose and the first head pose, and warp the enhanced image based on the difference between the second head pose and the first head pose to correct for head motion of the user.

Abstract: A system and method onboard an aircraft generates pilot awareness of obstacle clearance during an engine out (EO) go around (GA) situation. The system herein receives inputs from either a pilot selection or aircraft state change indicating a GA below a published missed approach altitude and also receives an input from an engine status monitor indicating an EO situation. As a GA below the published missed approach altitude does not ensure obstacle clearance with an EO, the systems herein generate a pseudo engine out go around procedure (PEOGAP) which calculates a minimum climb gradient maintaining a minimum separation from all obstacles within an area bound by the published missed approach. Once generated, the systems herein display the PEOGAP to the pilot for adequate obstacle separation and pilot awareness.

Abstract: A communication system is described. The communication system includes a number of nodes which frequency hop without coordination from a frequency table. To establish communication, the nodes scan across a band for one or more signals of interest. The signals of interest include one or more of a synchronization signal, a control signal, and a traffic signal. When transmitting the signals of interest, the nodes determine one or more characteristic for the signal, such as a channel, based on a spectral occupancy of interferers in the band.

Abstract: An ejection seat may comprise a seatback, a headrest located at an upper end of the seatback, and a pitot tube rotatably coupled to the headrest. A pitot restraint assembly may be operably coupled to the pitot tube. The pitot restraint assembly may be configured to translate between a restrained state and a released state. The pitot tube may rotate from a stowed position to a deployed position in response to the pitot restraint assembly translating to the released state.

Abstract: A system and method to assist piloting an aircraft in landing phase is disclosed. The system includes a pseudo glide path calculation module that includes a processor and a memory communicatively coupled to the one processor and having instructions stored upon. The instructions, when executed by the processor, cause the one or more processors to receive coordinates for a runway, receive exit path coordinates for a runway, receive aircraft configuration data, receive aircraft status data, receive runway environmental data, calculate a relative position of the aircraft in reference to the exit path coordinates and the runway environmental data, generate a pseudo displaced threshold for the runway, and generate a pseudo approach glide path profile based on the pseudo displaced threshold. The pseudo displaced threshold and the pseudo approach glide path profile may be depicted on a display. A runway occupation time may also be calculated.

Abstract: One embodiment provides an apparatus for displaying an image comprising: a first optical substrate comprising at least one waveguide layer configured to propagate light in a first direction, wherein the at least one waveguide layer of the first optical substrate comprises at least one grating lamina configured to extract the light from the first substrate along the first direction; and a second optical substrate comprising at least one waveguide layer configured to propagate the light in a second direction, wherein the at least one waveguide layer of the second optical substrate comprises at least one grating lumina configured to extract light from the second substrate along the second direction, wherein the at least one grating lamina of at least one of the first and second optical substrates comprises an SBG in a passive mode.